EP3156630A1 - Systèmes et procédés destinés à faciliter l'amélioration de la puissance utile de turbine au moyen d'un générateur auxiliaire - Google Patents

Systèmes et procédés destinés à faciliter l'amélioration de la puissance utile de turbine au moyen d'un générateur auxiliaire Download PDF

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Publication number
EP3156630A1
EP3156630A1 EP16191832.1A EP16191832A EP3156630A1 EP 3156630 A1 EP3156630 A1 EP 3156630A1 EP 16191832 A EP16191832 A EP 16191832A EP 3156630 A1 EP3156630 A1 EP 3156630A1
Authority
EP
European Patent Office
Prior art keywords
rotor shaft
auxiliary
primary
generator
coupled
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16191832.1A
Other languages
German (de)
English (en)
Inventor
Joseph Philip Klosinski
Alston Ilford Scipio
James Oldham Lambert
Karl TORNROOS
Sanji Ekanayake
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP3156630A1 publication Critical patent/EP3156630A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/12—Combinations with mechanical gearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/406—Transmission of power through hydraulic systems

Definitions

  • the field of the invention relates generally to turbine engines, and more particularly to systems and methods of using an auxiliary generator to facilitate improving operation of an existing primary generator.
  • At least some known turbine engines include a generator to produce electric energy.
  • improving the power factor in the generator facilitates improving the turbine performance.
  • increasing the power factor may cause the existing generator's capability to be exceeded. As such, the benefits of upgrading the turbine may be limited by the generator.
  • turbine assemblies may require generator re-wind or the installation of a new generator.
  • additional costs associated with extensive outage durations and/or new generators may make it prohibitively expensive to retrofit or replace generators.
  • other turbine assemblies include a second serial auxiliary/pony generator coupled in line with the primary generator.
  • auxiliary generator coupled in line with the primary generator.
  • a gas turbine engine system in one aspect, includes a gas turbine engine with a rotating element, at least one primary rotor shaft coupled to the rotating element, and a primary generator coupled to the at least one primary rotor shaft.
  • the system further includes at least one auxiliary rotor shaft coupled to the at least one primary rotor shaft, such that rotation of the at least one primary rotor shaft causes rotation of the at least one auxiliary rotor shaft.
  • the at least one auxiliary rotor shaft is oriented substantially perpendicularly to the at least one primary rotor shaft.
  • An auxiliary generator is coupled to the at least one auxiliary rotor shaft, such that the auxiliary generator is in parallel configuration to the primary generator.
  • a power generating system in another aspect, includes a turbine engine assembly comprising a gas turbine engine with a rotating element and at least one primary rotor shaft coupled to the rotating element.
  • the system further includes a generator assembly comprising a primary generator coupled to the at least one primary rotor shaft.
  • the generator assembly also includes at least one auxiliary rotor shaft coupled to the at least one primary rotor shaft, such that rotation of the at least one primary rotor shaft causes rotation of the at least one auxiliary rotor shaft.
  • the at least one auxiliary rotor shaft is oriented substantially perpendicularly to the at least one primary rotor shaft.
  • An auxiliary generator is coupled to the at least one auxiliary rotor shaft, such that the auxiliary generator is in parallel configuration to the primary generator.
  • at least one energy transmission mechanism is coupled between the at least one primary rotor shaft and the at least one auxiliary rotor shaft.
  • FIG. 1 is a schematic diagram of an exemplary gas turbine system 1.
  • gas turbine system 1 includes a turbine engine 10. More specifically, in the exemplary embodiment turbine engine 10 is a gas turbine that includes a compressor section 14, a combustor section 16 coupled downstream from compressor section 14, a turbine section 18 coupled downstream from combustor section 16, and an exhaust section 20 coupled downstream from turbine section 18.
  • turbine section 18 is coupled to compressor section 14 via a rotor assembly 22.
  • the term “couple” is not limited to a direct mechanical, electrical, and/or communication connection between components, but may also include an indirect mechanical, electrical, and/or communication connection between multiple components.
  • compressor section 14 receives an air flow 12.
  • Compressor section 14 converts mechanical rotation energy from rotor assembly 22 to compress air flow 12 to a higher pressure and temperature.
  • Compressor section 14 discharges a flow of compressed air 24 to combustor section 16.
  • compressed air 24 is mixed with a flow of fuel 26 and ignited to generate combustion gases 28 that are channeled towards turbine section 18.
  • Turbine section 18 converts thermal energy from combustion gases 28 to mechanical rotation energy of rotor assembly 22.
  • turbine 18 is a rotating element 48.
  • Rotor assembly 22 is coupled to a load such as, but not limited to, a primary electrical generator 30 and/or a mechanical drive application (not shown) via at least one primary rotor shaft 38.
  • primary rotor shaft 38 is coupled to an auxiliary rotor shaft 36, such that rotation of primary rotor shaft 38 causes rotation of auxiliary rotor shaft 36.
  • primary rotor shaft 38 and auxiliary rotor shaft 36 are oriented substantially perpendicularly to each other.
  • auxiliary rotor shaft 36 is illustrated as being substantially perpendicular to primary rotor shaft 38, in alternative embodiments, primary rotor shaft 38 and auxiliary rotor shaft 36 may be oriented at any suitable angle relative to each other that enables transfer of mechanical rotational energy as described herein.
  • an auxiliary/pony generator 32 is coupled to auxiliary rotor shaft 36 such that auxiliary generator 32 is in a parallel configuration to primary generator 30.
  • parallel configuration is not limited to a geometric relationship, but may also include multiple components, such as generators, that are not connected along a single path.
  • primary rotor shaft 38 is coupled to auxiliary rotor shaft 36 via an energy transmission mechanism 34. More specifically, in the exemplary embodiment at least a first energy transmission mechanism 34 is coupled between primary rotor shaft 38 and auxiliary rotor shaft 36. Energy transmission mechanism 34 enables the partial or full transfer of rotational energy from primary rotor shaft 38 to auxiliary rotor shaft 36. For example, output from gas engine turbine 10 not realized by primary generator 30, is realized by auxiliary generator 32 through transfer of mechanical rotational energy by auxiliary rotor shaft 36.
  • energy transmission mechanism 34 is a mechanical gear box, such as, but not limited to, a hydraulic clutch assembly, a splined quill shaft, a bevel gear, and speed reducing gears. In alternative embodiments, energy transmission mechanism 34 may include a different transmission mechanism, such as, but not limited to, a hydraulic gear box.
  • auxiliary rotor shaft 36 is between turbine 18 and primary generator 30.
  • energy transmission mechanism 34 is between turbine 18 and primary generator 30.
  • both auxiliary rotor shaft 36 and energy transmission mechanism 34 are illustrated as being on turbine 18 side of gas turbine engine 10, in alternative embodiments, both auxiliary rotor shaft 36 and energy transmission mechanism 34 may be located on the compressor 14 side of gas turbine engine 10, as described in further detail with respect to FIG. 4 below.
  • attachment of auxiliary rotor shaft 36 includes modifying primary rotor shaft 38 and integrating energy transmission mechanism 34.
  • an existing primary rotor shaft 38 is split to enable the introduction of energy transmission mechanism 34 and auxiliary rotor shaft 36.
  • primary rotor shaft 38 is manufactured as a replacement part for the introduction of energy transmission mechanism 34.
  • a power generator system 50 generally includes gas turbine engine 10, rotating element 48, and primary rotor shaft 38 coupled to rotating element 48.
  • a generator assembly 52 includes primary generator 30 coupled to primary rotor shaft 38, auxiliary rotor shaft 36 coupled to primary rotor shaft 38, auxiliary generator 32 coupled to auxiliary rotor shaft 36, and energy transmission mechanism 34.
  • a method of assembling a gas turbine engine system 1 includes providing gas turbine engine 10 with rotating element 48. Coupling primary rotor shaft 38 to rotating element 48 and coupling primary generator 30 to primary rotor shaft 38. Coupling auxiliary rotor shaft 36 to primary rotor shaft 38, such that rotation of primary rotor shaft 38 causes rotation of auxiliary rotor shaft 36, and auxiliary shaft 36 is oriented substantially perpendicularly to primary rotor shaft 38. Coupling auxiliary generator 32 to auxiliary rotor shaft 36, such that auxiliary generator 32 is in parallel configuration with primary generator 30. The method also includes coupling auxiliary rotor shaft 36 to primary rotor shaft 38 via energy transmission mechanism 34.
  • auxiliary rotor shaft 36 is coupled to primary rotor shaft 38 either between turbine 18 and primary generator 30, as illustrated in FIG. 1 , or such that primary generator 30 is between turbine 18 and auxiliary rotor shaft 36 as described in further detail with respect to FIG. 3 below.
  • FIG. 2 is a schematic diagram of an alternative gas turbine system 2.
  • turbine engine 10 is coupled to primary generator 30.
  • a first auxiliary rotor shaft 42 is coupled to primary rotor shaft 38 with a first energy transmission mechanism 34.
  • a second energy transmission mechanism 44 is coupled to an end of first auxiliary rotor shaft 42 opposite of first energy transmission mechanism 34.
  • a second auxiliary rotor shaft 46 is coupled to second energy transmission mechanism 44 such that the first and second auxiliary rotor shafts 42, 46 are oriented substantially perpendicularly to each other.
  • Auxiliary generator 32 is coupled to second auxiliary rotor shaft 46 opposite of second energy transmission mechanism 44.
  • first auxiliary rotor shaft 42 is illustrated as being substantially perpendicular to second auxiliary rotor shaft 46, in alternative embodiments, first auxiliary rotor shaft 42 and second auxiliary rotor shaft 46 may be oriented at any suitable angle relative to each other that enables transfer of mechanical rotational energy as described herein.
  • auxiliary generator 32 is coupled to first and second auxiliary rotor shafts 42, 46 such that auxiliary generator 32 is in a parallel configuration to primary generator 30.
  • second energy transmission mechanism 44 is coupled to an end of first auxiliary rotor shaft 42 of at least one auxiliary rotor shaft 36 opposite first energy transmission mechanism 34.
  • a second auxiliary rotor shaft 46 of at least one auxiliary rotor shaft 36 is coupled to second energy transmission mechanism 44 such that both first and second auxiliary rotor shafts 42, 46 are oriented substantially perpendicularly to each other.
  • the method for assembling gas turbine engine system 2 includes coupling second energy transmission mechanism 44 to end of first auxiliary rotor shaft 42 of at least one auxiliary rotor shaft 36 opposite first energy transmission mechanism 34. Also, coupling second auxiliary rotor shaft 46 of at least one auxiliary rotor shaft 36 to second energy transmission mechanism 44 such that both first and second auxiliary rotor shafts 42, 46 are oriented substantially perpendicularly to each other.
  • auxiliary rotor shaft 36 includes a first auxiliary rotor shaft 42 and second auxiliary rotor shaft 46 coupled together and transferring mechanical rotation energy as described herein from primary rotor shaft 38, through at least one auxiliary rotor shaft 36, and into auxiliary generator 32. Additionally, the first and second energy transmission mechanisms 34, 44 cause the partial or full transfer of mechanical rotational energy from each shaft member connected with.
  • both first and second energy transmission mechanisms 34, 44 is a mechanical gear box, such as, but not limited to a hydraulic clutch assembly, a splined quill shaft, a bevel gear, and speed reducing gear.
  • both first and second energy transmission mechanisms 34, 44 may include a different transmission mechanism, such as but not limited to, a hydraulic gear box. Also in alternate embodiments each energy transmission mechanism may be a similar type energy transmission mechanism, or may be a different type energy transmission mechanism.
  • first auxiliary rotor shaft 42 is between turbine 18 and primary generator 30.
  • first energy transmission mechanism 34 is between turbine 18 and primary generator 30.
  • first auxiliary rotor shaft 42 and first energy transmission mechanism 34 are illustrated as being on turbine 18 side of gas turbine engine 10, in alternative embodiments, both first auxiliary rotor shaft 42 and first energy transmission mechanism 34 may be located on the compressor 14 side of gas turbine engine 10, as described in further detail with respect to FIG. 4 below.
  • power generator system 50 generally includes gas turbine engine 10, rotating element 48, and primary rotor shaft 38 coupled to rotating element 48 as described above in reference to FIG. 1 .
  • a generator assembly 54 includes first and second auxiliary rotor shafts 42, 46 coupled to primary rotor shaft 38, and auxiliary generator 32 coupled to first and second auxiliary rotor shafts 42, 46.
  • First energy transmission mechanism 34 coupled between primary rotor shaft 38 and first auxiliary rotor shaft 42.
  • Generator assembly 54 further includes second energy transmission mechanism 44 coupled to first auxiliary rotor shaft 42 opposite first energy transmission mechanism 34, and second auxiliary rotor shaft 46 coupled to second energy transmission mechanism 44.
  • FIG. 3 is a schematic diagram of a second alternative gas turbine system 3.
  • a turbine engine 10 is coupled to primary generator 30.
  • first auxiliary rotor shaft 42 is coupled to primary rotor shaft 38.
  • Energy transmission mechanism 34 is coupled to an end of first auxiliary rotor shaft 42 opposite of primary generator 30.
  • Second auxiliary rotor shaft 46 is coupled to energy transmission mechanism 34 such that the first and second auxiliary rotor shafts 42, 46 are oriented substantially perpendicularly to each other.
  • Auxiliary generator 32 is coupled to second auxiliary rotor shaft 46 opposite of energy transmission mechanism 34.
  • first auxiliary rotor shaft 42 is illustrated as being substantially perpendicular to second auxiliary rotor shaft 46, in alternative embodiments, first auxiliary rotor shaft 42 and second auxiliary rotor shaft 46 may be oriented at any suitable angle relative to each other that enables transfer of mechanical rotational energy as described herein.
  • auxiliary generator 32 is coupled to first and second auxiliary rotor shafts 42, 46 such that auxiliary generator 32 is in a parallel configuration to primary generator 30.
  • primary generator 30 is between turbine 18 and first auxiliary rotor shaft 42. Also in the exemplary embodiment, primary generator 30 is between turbine 18 and energy transmission mechanism 34. Although both first auxiliary rotor shaft 42 and energy transmission mechanism 34 are illustrated as being on turbine 18 side of gas turbine engine 10, in alternative embodiments, both first auxiliary rotor shaft 42 and energy transmission mechanism 34 may be located on the compressor 14 side of gas turbine engine 10, as described in further detail with respect to FIG. 4 below.
  • power generator system 50 generally includes gas turbine engine 10, rotating element 48, and primary rotor shaft 38 coupled to rotating element 48 as described above in reference to FIG. 1 .
  • a generator assembly 56 includes first and second auxiliary rotor shafts 42, 46 coupled to primary rotor shaft 38, and auxiliary generator 32 coupled to first and second auxiliary rotor shafts 42, 46.
  • First energy transmission mechanism 34 coupled between first auxiliary rotor shaft 42 and second auxiliary rotor shaft 46.
  • FIG. 4 is a schematic diagram of a third alternative gas turbine system 4.
  • a turbine engine 10 is coupled to primary generator 30.
  • the primary generator 30, primary rotor shaft 38, energy transmission mechanism 34, auxiliary generator 32, and auxiliary rotor shaft 36 are located on the compressor 14 side of gas turbine engine 10.
  • compressor 14 is a rotating element 48.
  • power generator system 50 generally includes gas turbine engine 10, rotating element 48, and primary rotor shaft 38 coupled to rotating element 48 as described above in reference to FIG. 1 .
  • a generator assembly 52 includes primary generator 30 coupled to primary rotor shaft 38, auxiliary rotor shaft 36 coupled to primary rotor shaft 38, auxiliary generator 32 coupled to auxiliary rotor shaft 36, and energy transmission mechanism 34 as also described above in reference to FIG. 1 .
  • Exemplary embodiments of the gas turbine engine system and the power generation system include an auxiliary rotor shaft, an energy transmission mechanism, and an auxiliary generator in parallel configuration are described above in detail. Additionally, and the method for assembling the gas turbine system with an auxiliary generator in parallel configuration, is described above in detail.
  • the exemplary embodiments provide advantages in realizing mechanical output from the turbine engine. Extensive outage durations for the turbine and generator are not required thereby reducing costs. Retrofitting or replacing generators is also not required thereby reducing costs.
  • the exemplary embodiments eliminate the need to physically displace either turbine and/or primary generator reducing costs and down time. Providing an auxiliary generator in parallel configuration facilitates improving operation of the existing primary generator. As such, the benefits of upgrading the turbine are not limited by the primary generator.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Eletrric Generators (AREA)
EP16191832.1A 2015-10-15 2016-09-30 Systèmes et procédés destinés à faciliter l'amélioration de la puissance utile de turbine au moyen d'un générateur auxiliaire Withdrawn EP3156630A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/883,658 US20170107845A1 (en) 2015-10-15 2015-10-15 Systems and methods to facilitate enhancing turbine output using an auxiliary generator

Publications (1)

Publication Number Publication Date
EP3156630A1 true EP3156630A1 (fr) 2017-04-19

Family

ID=57240793

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16191832.1A Withdrawn EP3156630A1 (fr) 2015-10-15 2016-09-30 Systèmes et procédés destinés à faciliter l'amélioration de la puissance utile de turbine au moyen d'un générateur auxiliaire

Country Status (4)

Country Link
US (1) US20170107845A1 (fr)
EP (1) EP3156630A1 (fr)
JP (1) JP2017078411A (fr)
CN (1) CN107013328A (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440747A (en) * 2006-08-10 2008-02-13 Rolls Royce Plc Hydrodynamic coupling with movable turbine for engine power take off
WO2009067048A1 (fr) * 2007-11-20 2009-05-28 Volvo Aero Corporation Moteur à turbine à gaz
WO2014020104A1 (fr) * 2012-08-03 2014-02-06 Nuovo Pignone Srl Turbine à gaz à entraînement par les deux extrémités
EP2728141A2 (fr) * 2012-11-06 2014-05-07 Rolls-Royce plc Système de production électrique pour aéronef
EP2781720A1 (fr) * 2013-03-19 2014-09-24 Siemens Aktiengesellschaft Centrale électrique et procédé de production d'énergie électrique et alimentation du réseau
CN204316102U (zh) * 2015-01-14 2015-05-06 华电莱州发电有限公司 变频发电机组与汽轮发电机组同轴布置的火电厂发电机组

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3622022A1 (de) * 1986-07-01 1988-01-07 Kloeckner Humboldt Deutz Ag Gasturbinentriebwerk
US7791235B2 (en) * 2006-12-22 2010-09-07 General Electric Company Variable magnetic coupling of rotating machinery
GB0903423D0 (en) * 2009-03-02 2009-04-08 Rolls Royce Plc Variable drive gas turbine engine
GB2474286B (en) * 2009-10-12 2011-08-31 Rolls Royce Plc A propulsion engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440747A (en) * 2006-08-10 2008-02-13 Rolls Royce Plc Hydrodynamic coupling with movable turbine for engine power take off
WO2009067048A1 (fr) * 2007-11-20 2009-05-28 Volvo Aero Corporation Moteur à turbine à gaz
WO2014020104A1 (fr) * 2012-08-03 2014-02-06 Nuovo Pignone Srl Turbine à gaz à entraînement par les deux extrémités
EP2728141A2 (fr) * 2012-11-06 2014-05-07 Rolls-Royce plc Système de production électrique pour aéronef
EP2781720A1 (fr) * 2013-03-19 2014-09-24 Siemens Aktiengesellschaft Centrale électrique et procédé de production d'énergie électrique et alimentation du réseau
CN204316102U (zh) * 2015-01-14 2015-05-06 华电莱州发电有限公司 变频发电机组与汽轮发电机组同轴布置的火电厂发电机组

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CN107013328A (zh) 2017-08-04
JP2017078411A (ja) 2017-04-27
US20170107845A1 (en) 2017-04-20

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